JP6186150B2

JP6186150B2 - Proximity channel seal isolation dovetail

Info

Publication number: JP6186150B2
Application number: JP2013065334A
Authority: JP
Inventors: マシュー・ロバート・ピアーソル; ブライアン・デンバー・ポッター
Original assignee: General Electric Co
Current assignee: General Electric Co
Priority date: 2012-03-29
Filing date: 2013-03-27
Publication date: 2017-08-23
Anticipated expiration: 2033-03-27
Also published as: US20130259700A1; RU2013113929A; US9151169B2; EP2644832A1; JP2013204595A; CN103362561A; CN103362561B; EP2644832B1

Description

本発明は、全体的に、燃焼技術に関し、より具体的には、燃焼タービンの高温ガス経路内の回転構成要素と固定構成要素との間のシール構成に関する。 The present invention relates generally to combustion technology, and more specifically to a seal arrangement between a rotating component and a stationary component in a hot gas path of a combustion turbine.

通常、近接流路シールは、近隣のノズルの直ぐ下にあるバケットの隣接する段の間に位置付けられる。より具体的には、近接流路シールは、タービンバケットの周辺列を支持する隣接するホイール又はディスク間に軸方向に位置付けられたスペーサホイール又はディスクに装填される。近接流路シールは、スペーサホイールから反対方向で軸方向に延びて、ノズルの下方に流路を形成し、また、高温燃焼ガスを半径方向内側ホイールスペースの外に保持するアームを有する。但し、近接流路シールの軸方向アームは、自立型ではなく、各アームは、タービンが通常運転状態にあって且つタービンロータの回転に伴って作用する遠心方向の力に曝されたときに荷重面を必要とする。典型的な構成では、近接流路シールは、３つの箇所、すなわち、ダブテールを通る近隣ホイール間にあるスペーサホイール上及び２つの隣接するバケットの荷重表面（通常は、それぞれのバケット上の一体型カバープレートの表面）上にて装填される。 Typically, the proximity channel seal is positioned between adjacent stages of the bucket just below the neighboring nozzles. More specifically, the proximity flow path seals are loaded into spacer wheels or disks positioned axially between adjacent wheels or disks that support the peripheral rows of turbine buckets. The proximal flow path seal extends axially in the opposite direction from the spacer wheel to form a flow path below the nozzle and has an arm that holds the hot combustion gases out of the radially inner wheel space. However, the axial arm of the adjacent flow path seal is not self-supporting, and each arm is loaded when the turbine is in a normal operating state and exposed to centrifugal force acting as the turbine rotor rotates. Need a plane. In a typical configuration, the proximity flow path seals are located at three locations: on the spacer wheel between neighboring wheels through the dovetail and on the load surface of two adjacent buckets (usually an integral cover on each bucket). Loaded on the surface of the plate).

従って、隣接バケットへの荷重（例えば、遠心方向及び／又は軸方向で）を改善する近接流路シール設計に対する要求が依然としてある。 Thus, there is still a need for a proximity channel seal design that improves the load on adjacent buckets (eg, in the centrifugal and / or axial direction).

米国特許第６，６５２，２３７号明細書US Pat. No. 6,652,237

例示的で非限定的な実施形態によれば、翼形部分と、翼形部分の半径方向内向きにあるプラットフォームと、プラットフォームの半径方向内向きにあるシャンク部と、シャンク部の半径方向内向きにある取り付け部と、を備えたタービンバケットが提供され、シャンク部が、少なくとも１つの軸方向に延びる近接流路シール係合面を有し、該近接流路シール係合面と取り付け部の一部がタービンバケットから分離可能な隔離要素を形成する。 According to an exemplary, non-limiting embodiment, an airfoil portion, a platform that is radially inward of the airfoil portion, a shank portion that is radially inward of the platform, and a radially inward direction of the shank portion And a shank portion having at least one axially extending proximal channel seal engaging surface, wherein the proximal channel seal engaging surface and one of the mounting portions are provided. The part forms an isolation element separable from the turbine bucket.

別の態様において、スペーサディスクが軸方向で間に位置付けられた少なくとも２つのロータディスクを備え、該各ロータディスクがバケットの環状列を備えている、タービンロータ組立体が提供され、該各バケットが、翼形部分と、翼形部分の半径方向内向きにあるプラットフォームと、プラットフォームの半径方向内向きにあるシャンク部と、シャンク部の半径方向内向きにある取り付け部と、を含み、シャンク部が少なくとも１つの近接流路シール係合面を有し、該近接流路シール係合面と取り付け部の一部が前記タービンバケットから分離可能な隔離要素を形成する。 In another aspect, a turbine rotor assembly is provided in which a spacer disk comprises at least two rotor disks positioned axially therebetween, each rotor disk comprising an annular row of buckets, each bucket comprising: An airfoil portion, a platform radially inward of the airfoil portion, a shank portion radially inward of the platform, and a mounting portion radially inward of the shank portion, the shank portion comprising: It has at least one proximity channel seal engagement surface, and the proximity channel seal engagement surface and a portion of the attachment form an isolation element separable from the turbine bucket.

更に別の態様において、タービンバケット上に形成される隣接する表面部分と近接流路シールとの係合によって引き起こされるタービンバケット上の遠心方向又は軸方向の荷重を低減する方法が提供され、該方法が、隣接表面部分を含む前記バケットから材料を除去して切り出し部を形成するステップと、切り出し部に一致し且つタービンの作動中に近接流路シールと係合可能な隔離要素で材料を置き換えるステップと、を含む。 In yet another aspect, a method is provided for reducing centrifugal or axial loads on a turbine bucket caused by engagement of adjacent surface portions formed on the turbine bucket with a proximity flow path seal. Removing material from the bucket including adjacent surface portions to form a cutout, and replacing the material with an isolating element that matches the cutout and engages the proximal flow path seal during operation of the turbine. And including.

ここで、以下に示された図面に関して本発明をより詳細に説明する。 The invention will now be described in more detail with reference to the drawings shown below.

従来構成におけるバケットの隣接列間に位置付けられた近接流路シールの簡易側面図。The simple side view of the proximity | contact channel | path seal | sticker located between the adjacent rows of the bucket in a conventional structure. 図１からの拡大詳細図。FIG. 2 is an enlarged detail view from FIG. 1. 図２に類似するが、本発明の例示的で非限定的な実施形態による近接流路シール構成を示した図。FIG. 3 is a view similar to FIG. 2 but illustrating a near flow path seal configuration according to an exemplary, non-limiting embodiment of the present invention. 例示的で非限定的な実施形態による、切り出し部を備えて形成されたバケットの半径方向内側端部の拡大詳細図。FIG. 4 is an enlarged detail view of a radially inner end of a bucket formed with a cutout, according to an exemplary, non-limiting embodiment. 図４に示すバケットの半径方向内側端部からの切り出し部、又は、図４に示すバケットの半径方向内側部分から除去した部分の形状に一致する別個に製造された部分（すなわち、隔離要素）の斜視図。4. A cutout from the radially inner end of the bucket shown in FIG. 4 or a separately manufactured portion (ie, an isolation element) that matches the shape of the portion removed from the radially inner portion of the bucket shown in FIG. Perspective view. 図４に類似するが、バケットの半径方向内側端部の切り出し部内に示した隔離要素の部分斜視図。FIG. 5 is a partial perspective view of the isolation element similar to FIG. 4 but shown in a cutout at the radially inner end of the bucket.

図１及び２は、公知の近接流路シール構成を示す。具体的には、近接流路シール１０は、スペーサディスクと固定ノズル１４との間に半径方向でスペーサディスク又はホイール１２上に位置付けられる。近接流路シール１０は、半径方向に延びる複数のシール歯１５と、反対方向に突出して隣接するバケット２４、２６それぞれ上の近接流路シール係合面２０、２２と相互作用するようになる軸方向に延びるシールアーム１６、１８とを含むように図示されている。図２において最も分かるように、近接流路シール１０のアーム１６、１８は、バケットシール係合面２０、２２の直ぐ下（又は半径方向内向き）に位置付けられる。近接流路シール１０のアーム１６、１８は支持されておらず、タービンの通常運転中はシール係合面２０、２２それぞれの底面を係合し、これによりこれらの面が、例えば、タービンロータの回転及び熱的成長の差違に起因した軸方向及び遠心方向の力に曝されるようになる。 1 and 2 show a known proximity channel seal configuration. Specifically, the proximity flow path seal 10 is positioned on the spacer disk or wheel 12 in the radial direction between the spacer disk and the fixed nozzle 14. The adjacent flow path seal 10 has a plurality of radially extending seal teeth 15 and an axis that protrudes in the opposite direction and interacts with adjacent flow path seal engaging surfaces 20 and 22 on adjacent buckets 24 and 26, respectively. Illustrated to include directionally extending seal arms 16, 18. As best seen in FIG. 2, the arms 16, 18 of the proximity channel seal 10 are positioned just below (or radially inward) the bucket seal engagement surfaces 20, 22. The arms 16, 18 of the proximity channel seal 10 are not supported and engage the bottom surfaces of the seal engagement surfaces 20, 22 during normal operation of the turbine so that these surfaces, for example, of the turbine rotor Be exposed to axial and centrifugal forces due to differences in rotation and thermal growth.

近接流路シール係合面２０、２２は、バケットカバープレート又は半径方向に隣接するエンジェルウィングシールと独立した他の表面上に設けることができる。 Proximal flow path seal engagement surfaces 20, 22 may be provided on the bucket cover plate or other surface independent of the radially adjacent angel wing seal.

この公知の構成では、バケットカバープレート又は他のシール２０、２２上にアーム１６、１８によって作用する荷重は、バケット２４、２６に直接伝達され、従って、バケットに対する望ましくない応力又はロータシステムにおける剛性を生じる点は理解されるであろう。 In this known configuration, the load exerted by the arms 16, 18 on the bucket cover plate or other seals 20, 22 is transmitted directly to the buckets 24, 26, thus reducing undesirable stress on the buckets or stiffness in the rotor system. The point that will occur will be understood.

図３〜６を参照すると、本発明の例示的で非限定的な実施形態において、隣接バケット３４、３６に対する近接流路シール３２の全体構成は、図２に示す構成と同様である。以下の説明では、近接流路シール３８及び隣接バケット３６に焦点を当てているが、バケット荷重問題に対する解決策は、シールアーム４０及び隣接バケット３４にも、並びに種々のタービン段間の他の何れかの近接流路シールにも同様に適用可能である点は理解されるであろう。例示的な実施形態において、バケット３６は、破線４６で輪郭が描かれたダブテール部分４２及びシャンク部４４の軸方向端部から材料を除去することにより修正され、結果として得られる切り出し部４８は、図４において最もよく分かる。具体的には、切り出し部４８は、エンジェルウィングシール５０の下側部分、ダブテール取り付け部４２及びシャンク部４４の一部、並びに翼形部分５２及びプラットフォーム５４の半径方向内向きの部分を除去することによって形成される。隔離要素５６は、エンジェルウィングシール５０の最も低い又は半径方向内側の表面５８を提供するように形成され、また、バケットのダブテール取り付け部４２の輪郭に一致するダブテール取り付け部６０を提供するように形成される。これにより、隔離要素５６をバケットダブテール部分４２と共にロータディスク内に形成されたダブテールスロットに装填できるようになる。換言すると、切り出し部４８は、切り出し部４８から除去された部分と実質的に同じ形状を有する隔離要素で充填されるが、隔離要素とバケットとの間にはギャップが存在してもよい点に留意されたい。 With reference to FIGS. 3-6, in an exemplary, non-limiting embodiment of the present invention, the overall configuration of the proximal flow path seal 32 relative to adjacent buckets 34, 36 is similar to the configuration shown in FIG. Although the following discussion focuses on the proximity flow path seal 38 and adjacent bucket 36, solutions to the bucket load problem also apply to the seal arm 40 and adjacent bucket 34 as well as any other between the various turbine stages. It will be appreciated that the proximity channel seal is equally applicable. In the exemplary embodiment, bucket 36 is modified by removing material from the axial end of dovetail portion 42 and shank portion 44 outlined by dashed line 46 and the resulting cutout 48 is: This is best seen in FIG. Specifically, the cutout 48 removes the lower portion of the angel wing seal 50, a portion of the dovetail attachment portion 42 and the shank portion 44, and the radially inward portion of the airfoil portion 52 and platform 54. Formed by. Isolation element 56 is formed to provide the lowest or radially inner surface 58 of angel wing seal 50 and is configured to provide a dovetail attachment 60 that matches the contour of bucket dovetail attachment 42. Is done. This allows the isolation element 56 to be loaded into the dovetail slot formed in the rotor disk along with the bucket dovetail portion 42. In other words, the cutout 48 is filled with a separating element having substantially the same shape as the portion removed from the cutout 48, but there may be a gap between the separating element and the bucket. Please keep in mind.

図６は、隔離要素５６がダブテール取り付け部４２及びエンジェルウィングシール５０の底面の当初の輪郭と一致した様子を示している。隔離要素５６が所定位置にあるときには、近接流路シールアーム３８は下側縁部５８と係合しており、隔離要素５６はもはやバケット３６から接続解除されているので、バケットは、作動中に近接流路シールアーム３８によって作用される力から隔離される。 FIG. 6 shows how the isolation element 56 matches the original contours of the bottom surface of the dovetail attachment 42 and angel wing seal 50. When the isolation element 56 is in place, the proximal flow path seal arm 38 is engaged with the lower edge 58 and the isolation element 56 is no longer disconnected from the bucket 36 so that the bucket is in operation. Isolated from the force exerted by the proximal flow path seal arm 38.

隔離要素５６は、バケット３６から除去される部分だけから構成することができ、又は、除去した材料と一致するよう形成された新規製造の要素とすることができる点は理解されるであろう。また、本明細書で説明される隔離特徴要素は、既存のバケットに後付けするか、又は新規製造のバケットに組み込むことができる点は理解されるであろう。 It will be appreciated that the isolation element 56 can be composed of only the portion that is removed from the bucket 36 or can be a newly manufactured element that is shaped to match the removed material. It will also be appreciated that the isolation features described herein can be retrofitted to existing buckets or incorporated into newly manufactured buckets.

バケットシール構造体と近接流路シールアームとの係合により生じることになる遠心方向の力を実質的に排除することにより、バケット寿命の延長を実現することができる。 By substantially eliminating the centrifugal force that is generated by the engagement of the bucket seal structure and the adjacent flow path seal arm, the extension of the bucket life can be realized.

現時点で最も実用的且つ好ましい実施形態であると考えられるものに関して本発明を説明してきたが、本発明は、開示した実施形態に限定されるものではなく、逆に添付の請求項の技術的思想及び範囲内に含まれる様々な修正形態及び均等な構成を保護するものであることを理解されたい。 Although the present invention has been described with respect to what is considered to be the most practical and preferred embodiments at the present time, the invention is not limited to the disclosed embodiments, and conversely, the technical spirit of the appended claims It should also be understood that various modifications and equivalent arrangements included within the scope are protected.

１０，３２近接流路シール
１２ディスク又はホイール
１４固定ノズル
１５シール歯
１６，１８シールアーム
２０，２２シール係合面
２４，２６，３４，３６バケット
２８，３０底面
３８，４０シールアーム
４２ダブテール部分
４４シャンク部
４６破線
４８切り出し部
５０エンジェルウィングシール
５２バケット翼形部
５４プラットフォーム
５６隔離要素
５８最も低い縁部又は半径方向内側表面 10, 32 Proximity flow path seal 12 Disc or wheel 14 Fixed nozzle 15 Seal teeth 16, 18 Seal arm 20, 22 Seal engagement surface 24, 26, 34, 36 Bucket 28, 30 Bottom 38, 40 Seal arm 42 Dovetail portion 44 Shank 46 Dotted line 48 Cutout 50 Angel wing seal 52 Bucket airfoil 54 Platform 56 Isolation element 58 Lowest edge or radially inner surface

Claims

A turbine bucket assembly that rotates about an axis of rotation comprising a turbine bucket, the turbine bucket comprising:
An airfoil part,
A platform located radially inward side of the airfoil portion,
A shank portion located radially inward side of the platform,
A dovetail portion radially inward of the shank portion;
An isolation element that is unconnected to the shank portion and the dovetail portion,
With
It said shank portion has an end region including the contact surface among which extends axially facing the shaft,
The axial end portion of the dovetail portion extending in the radius direction, a corner is formed between said inscribed surface of the shank portion and the axial end of the dovetail portion,
The isolation element, the axial extension plane extending parallel immediately adjacent to the inscribed surface of said shank portion, radially extending extending parallel immediately adjacent to the axial end of the dovetail portion Having a face,
Turbine bucket assembly .

The turbine bucket assembly of claim 1, wherein the isolation element has a cross-sectional profile that substantially matches a corresponding cross-sectional profile of the dovetail portion.

The turbine bucket assembly of claim 1, wherein the isolation element is received at a cutout formed in the bucket.

The turbine bucket assembly of claim 3, wherein the isolation element includes an element cut from the shank portion and the dovetail portion .

The turbine bucket assembly of claim 1, wherein the isolation element is engageable with a proximity flow path seal during operation of the turbine.

A turbine rotor assembly, wherein the spacer disk comprises at least two rotor disks positioned axially therebetween, each rotor disk comprising an annular row of buckets,
Each bucket is
An airfoil part,
A platform located radially inward side of the airfoil portion,
A shank portion located radially inward side of the platform,
A dovetail portion radially inward of the shank portion;
An isolation element,
With
It said shank portion has a angel wing seal a angel wing seal having a semi-radial inner surface facing the axis extending in the direction of the axis of the turbine rotor assembly,
Before SL dovetail portion includes a radial extending face in the axial end portion,
The isolation element includes a radially outer surface directly adjacent to the radially inner surface of the angel wing seals, radially extending immediately adjacent to the semi-radially extending surface on said axial end of the dovetail portion And having a surface,
The isolation element is isolated and disconnected from the shank portion and the dovetail portion;
Turbine rotor assembly.

The turbine rotor assembly of claim 6 , wherein the isolation element has a cross-sectional profile that substantially matches a corresponding cross-sectional profile of the dovetail.

The turbine rotor assembly of claim 6 , wherein the isolation element is received at a cutout formed in the bucket.

The turbine rotor assembly of claim 8 , wherein the isolation element includes elements cut from a portion of the turbine bucket shank and dovetail and a lower portion of the angel wing seal.

The turbine rotor assembly of claim 6 , wherein the isolation element is engageable with a proximity flow path seal during operation of the turbine.

A method for reducing centrifugal or axial loads on said turbine bucket caused by engagement of adjacent surface portions formed on a turbine bucket with a proximity flow path seal, comprising:
Removing material from the bucket including the adjacent surface portion to form a cutout (a);
Replacing the material with an isolation element that coincides with the cutout radially inward of the platform of the bucket;
Including
The isolation element has a radially inner portion extending in the axial direction of an angel wing seal having a radially extending portion on the axial end of the dovetail portion and a proximal channel seal engaging surface;
The isolation element is unconnected and immediately adjacent to an axially extending radially inner surface of the angel wing seal and a radially extending surface on the dovetail portion of the turbine bucket;
The isolation element is engageable with said near-flow-path seal during operation of the turbines,
Method.

The method of claim 11 , comprising manufacturing the isolation element separately from the turbine bucket.

The method of claim 12 , wherein step (a) includes removing material from a portion of the bucket shank and dovetail portion and the bottom of the angel wing seal.

The method of claim 13 , wherein the isolation element matches a cross-sectional profile of the material removed from the bucket.

The method of claim 11 , wherein step (b) comprises utilizing the material removed from the bucket as the isolation element.